EP3121430A1 - Ensemble de nacelle - Google Patents

Ensemble de nacelle Download PDF

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Publication number
EP3121430A1
EP3121430A1 EP16180579.1A EP16180579A EP3121430A1 EP 3121430 A1 EP3121430 A1 EP 3121430A1 EP 16180579 A EP16180579 A EP 16180579A EP 3121430 A1 EP3121430 A1 EP 3121430A1
Authority
EP
European Patent Office
Prior art keywords
wall
fan
axial length
engine
nacelle assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP16180579.1A
Other languages
German (de)
English (en)
Other versions
EP3121430B1 (fr
Inventor
Frederick M. Schwarz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP3121430A1 publication Critical patent/EP3121430A1/fr
Application granted granted Critical
Publication of EP3121430B1 publication Critical patent/EP3121430B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/80—Repairing, retrofitting or upgrading methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/60—Structure; Surface texture
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within

Definitions

  • the present disclosure is generally related to gas turbine engines and, more specifically, a nacelle assembly.
  • Gas turbine engines such as turbofan gas turbine engines, typically include a core engine having a fan section, a compressor section, a combustor section and a turbine section. During operation, air is pressurized in the compressor section and mixed with fuel in the combustor section for generating hot combustion gases. The hot combustion gases flow through the turbine section which extracts energy from the hot combustion gases to power the compressor section and drive the fan section.
  • the core engine is generally surrounded by a nacelle assembly that is annularly disposed about the core engine.
  • the nacelle assembly and the engine casing structure cooperate to assemble the gas turbine engine.
  • an inlet lip assembly of the nacelle assembly is attached to an A-flange disposed about the fan section of the core engine.
  • a fan containment case (“FCC”) is attached to an opposite side of the A-flange from the inlet lip assembly.
  • FCC fan containment case
  • the A-flange permits assembly/disassembly of the inlet lip assembly from the FCC.
  • an engine electronic control is typically mounted aft of the fan containment case, such as on the fan case.
  • a fan section of a turbine engine includes a fan containment case within which a plurality of fan blades are contained.
  • the fan containment case is enclosed within an aerodynamic fan nacelle that at least partially surrounds an aerodynamic core nacelle.
  • the fan containment case and aerodynamic fan nacelle are supported by circumferentially spaced structures.
  • the fan containment case includes a first casing coupling member located on an outer surface forward of the fan blades, and a second casing coupling member located on the outer surface aft of the circumferentially spaced structures.
  • an engine accessory including an accessory axial length, is affixed to the outer surface of the fan containment case.
  • the engine accessory includes an electronic engine control.
  • the fan nacelle includes an inlet assembly operably coupled to a first nacelle flange.
  • the fan nacelle further includes an inner wall and an outer wall.
  • the inner wall includes an inner wall forward end, an inner wall aft end, and an inner wall axial length.
  • the inner wall aft end is configured to be operably coupled to the first casing coupling member.
  • the outer wall includes an outer wall forward end, an outer wall aft end, and an outer wall axial length.
  • the outer wall is monolithic.
  • the outer wall aft end is configured to be operably coupled to the second casing coupling member.
  • the fan nacelle includes a fan compartment cowling panel including a panel axial length.
  • the fan cowl panel is operably coupled to the outer wall aft end and the second casing coupling member.
  • the panel axial length is less than or equal to approximately three times the accessory axial length.
  • the fan compartment cowling panel includes an access opening disposed therein, wherein the access opening is located adjacent to the engine accessory.
  • a gas turbine engine including a fan section, the fan section comprising: a plurality of fan blades; a plurality of guide vanes positioned aft of the plurality of fan blades; a fan containment case circumferentially surrounding the plurality of fan blades and the plurality of guide vanes, the fan casing comprising a first casing coupling member located on an outer surface forward of the plurality of fan blades, and a second casing coupling member located on the outer surface aft of the plurality of guide vanes; and a fan nacelle assembly circumferentially surrounding the fan casing, the fan nacelle assembly comprising: an inner wall including an inner aft end, wherein the inner aft end is operably coupled to the first casing coupling member; an outer wall including an outer wall aft end, wherein the outer wall aft end is positioned aft of the first casing coupling member.
  • the outer wall is monolithic.
  • an engine accessory is affixed to the outer surface of the fan containment case, wherein the engine accessory includes an accessory axial length.
  • the outer wall further comprises an access opening disposed therein, wherein the access opening is located adjacent to the engine accessory.
  • the fan nacelle assembly further comprises a fan compartment cowling panel operably coupled to the outer wall aft end and the second casing coupling member, wherein the fan cowl panel includes a panel axial length.
  • the panel axial length is less than or equal to approximately three times the accessory axial length.
  • the fan compartment cowling panel further comprises an access opening disposed therein, wherein the access opening is located adjacent to the engine accessory.
  • a nacelle assembly for housing an aircraft jet engine including a fan section, the fan nacelle assembly comprising: an inner wall including an inner wall forward end, an inner wall aft end, and an inner wall axial length; and an outer wall including an outer wall forward end, an outer wall aft end, and an outer wall axial length; wherein the outer wall axial length is greater than the inner wall axial length.
  • the outer wall is monolithic.
  • the outer wall further comprises at least one access opening disposed therein.
  • a fan compartment cowling panel is operably coupled to the outer wall aft end.
  • the fan compartment cowling panel comprises at least one access opening disposed therein.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmentor section (not shown) among other systems or features.
  • the fan section 22 drives air along a bypass flow path B in a bypass duct, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28.
  • the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
  • the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 and a low pressure turbine 46.
  • the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54.
  • a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54.
  • An engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46.
  • the engine static structure 36 further supports bearing systems 38 in the turbine section 28.
  • the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
  • each of the positions of the fan section 22, compressor section 24, combustor section 26, turbine section 28, and fan drive gear system 48 may be varied.
  • gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.
  • the engine 20 in one example is a high-bypass geared aircraft engine.
  • the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
  • the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3
  • the low pressure turbine 46 has a pressure ratio that is greater than about five.
  • the engine 20 bypass ratio is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 44
  • the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1.
  • Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle
  • the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
  • the fan section 22 of the engine 20 is designed for a particular flight condition - typically cruise at about 0.8 Mach and about 35,000 feet (10,688 meters).
  • the flight condition of 0.8 Mach and 35,000 ft. (10,688 meters), with the engine at its best fuel consumption - also known as "bucket cruise Thrust Specific Fuel Consumption ('TSFC')" - is the industry standard parameter of Ibm of fuel being burned divided by Ibf of thrust the engine produces at that minimum point.
  • "Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
  • the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
  • Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)] 0.5 .
  • the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft / second (350.5 m/sec).
  • the fan section 22 generally includes a fan containment case 60 within which the fan blades 42 are contained.
  • the fan containment case 60 is enclosed within an aerodynamic fan nacelle 62 (illustrated schematically) that at least partially surrounds an aerodynamic core nacelle 64 (illustrated schematically).
  • the fan containment case 60 and aerodynamic fan nacelle 62 are supported by circumferentially spaced structures 66 often referred to as Fan Exit Guide Vanes (FEGVs).
  • FEGVs Fan Exit Guide Vanes
  • the fan containment case 60 includes a first casing coupling member 68, for example a flange, located on an outer surface 70 forward of the fan blades 42, and a second casing coupling member 72 located on the outer surface 70 aft of the circumferentially spaced structures 66 (not shown in FIG. 2 ).
  • the second casing coupling member 66 may be a flange or V-groove to name a couple of non-limiting examples.
  • an engine accessory 74 including an accessory axial length 76, is affixed to the outer surface 70 of the fan containment case 60.
  • the engine accessory 74 includes an electronic engine control.
  • the fan nacelle 62 includes an inlet assembly 78 operably coupled to a first nacelle flange 80.
  • the fan nacelle 62 further includes an inner wall 82; the inner wall 82 including an inner wall forward end 84, an inner wall aft end 86, and an inner wall axial length 87.
  • the inner wall forward end 84 is operably coupled to the first nacelle flange 80.
  • the inner wall aft end 86 is configured to be operably coupled to the first casing flange 68.
  • the fan nacelle 62 further includes an outer wall 88; the outer wall 88 including an outer wall forward end 90, an outer wall aft end 92, and an outer wall axial length 94.
  • the outer wall 88 is monolithic.
  • the outer wall forward end 90 is operably coupled to the first nacelle flange 80.
  • the outer wall aft end 92 is configured to be operably coupled to the second casing coupling member 72.
  • the outer wall axial length 94 is greater than the inner wall axial length 87. It will be appreciated that the fan nacelle 62 may have one or more support flanges 89 to provide stability between the inner wall 82 and the outer wall 88.
  • the outer wall 88 includes at least one access opening 96 (shown in FIG.3 ) disposed therein.
  • the at least one access opening 96 may include a small door, hatch or a panel capable of sliding in any direction to name a few non-limiting examples.
  • the at least one access opening 96 may be positioned adjacent to the engine accessory 74 to provide maintenance access thereto. It will be appreciated that multiple accesses openings 96 may be disposed in the outer wall to gain access to other accessories and/or wiring affixed to the outer surface 70 of the fan containment case 60.
  • the fan nacelle 62 includes a fan compartment cowling panel 98 including a panel axial length 100.
  • the fan compartment cowling panel 98 is operably coupled to the outer wall aft end 92 and the second casing coupling member 72.
  • the panel axial length 100 is less than or equal to approximately three times the accessory axial length 76. For example, if the engine accessory 74 has an accessory axial width 76 of approximately 13 inches (approximately 33 cm); then, the fan compartment cowling panel 98 would have a panel axial width 100 less than or equal to approximately 39 inches (99 cm).
  • the fan compartment cowling panel 98 includes an access opening 96 disposed therein, wherein the access opening 96 is located adjacent to the engine accessory 74.
  • the access opening 96 may include a small door, hatch or a panel capable of sliding in any direction, to name a few non-limiting examples.
  • the access opening 96 may be positioned adjacent to the engine accessory 74 to provide maintenance access thereto.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16180579.1A 2015-07-21 2016-07-21 Ensemble de nacelle Active EP3121430B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/804,728 US10590952B2 (en) 2015-07-21 2015-07-21 Nacelle assembly

Publications (2)

Publication Number Publication Date
EP3121430A1 true EP3121430A1 (fr) 2017-01-25
EP3121430B1 EP3121430B1 (fr) 2021-11-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16180579.1A Active EP3121430B1 (fr) 2015-07-21 2016-07-21 Ensemble de nacelle

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US (1) US10590952B2 (fr)
EP (1) EP3121430B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3587245A1 (fr) * 2018-06-29 2020-01-01 Airbus Operations Groupe propulseur d'aeronef comprenant un assemblage d'au moins deux arbres coaxiaux, l'un etant relie a la soufflante et l'autre a l'ensemble d'aubes fixes

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WO2014151097A1 (fr) * 2013-03-15 2014-09-25 United Technologies Corporation Boîtier composite renforce
WO2014200571A2 (fr) * 2013-02-19 2014-12-18 United Technologies Corporation Structure d'attachement composite à armure 3d
WO2015006445A1 (fr) * 2013-07-09 2015-01-15 United Technologies Corporation Nacelle en polymère plaqué

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EP0921293A1 (fr) * 1997-12-02 1999-06-09 Aerospatiale Societe Nationale Industrielle Dispositif d'évacuation d'air chaud pour capot d'entrée d'air de moteur à réaction à circuit de dégivrage
EP2628919A2 (fr) * 2012-02-20 2013-08-21 Rolls-Royce plc Nacelle pour système de propulsion d'aéronef
WO2014200571A2 (fr) * 2013-02-19 2014-12-18 United Technologies Corporation Structure d'attachement composite à armure 3d
WO2014151097A1 (fr) * 2013-03-15 2014-09-25 United Technologies Corporation Boîtier composite renforce
WO2015006445A1 (fr) * 2013-07-09 2015-01-15 United Technologies Corporation Nacelle en polymère plaqué

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3587245A1 (fr) * 2018-06-29 2020-01-01 Airbus Operations Groupe propulseur d'aeronef comprenant un assemblage d'au moins deux arbres coaxiaux, l'un etant relie a la soufflante et l'autre a l'ensemble d'aubes fixes
FR3083206A1 (fr) * 2018-06-29 2020-01-03 Airbus Operations Groupe propulseur d'aeronef comprenant un assemblage d'au moins deux arbres coaxiaux, l'un etant relie a la soufflante et l'autre a l'ensemble d'aubes fixes
CN110657045A (zh) * 2018-06-29 2020-01-07 空中客车运营简化股份公司 飞行器推进机组及具有这种推进机组的飞行器后部
US11708168B2 (en) 2018-06-29 2023-07-25 Airbus Operations (S.A.S.) Aircraft propulsion unit comprising an assembly of at least two coaxial shafts, one being connected to the fan and the other to the assembly of fixed blades

Also Published As

Publication number Publication date
EP3121430B1 (fr) 2021-11-03
US20170023012A1 (en) 2017-01-26
US10590952B2 (en) 2020-03-17

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